초음속 복합재료 날개의 변형특성

Abstract

Deformation characteristics in subsonic and supersonic speeds has been studied for the tapered backward swept wing with 45° leading edge sweep angle. Both isotropic aluminum wing and T300/5208 Graphite/Epoxy composite wing are examined to see wing flexibility effects. This analysis uses two methods. One is the finite element method(F.E.M) for the plate structural analysis and the other is the Gustavsson program based on Woodward panel method for the aerodynamic analysis. Two programs are combined by a surface spline interpolation procedure. The final deformed shape of wing due to applied aerodynamic forces is determined by iterative manner using FEM and Gustavsson program. The effect of compressibility and wing flexibility on the wing deformation in supersonic speed is discussed in this analysis. The wing deformation are greatly affected by the fiber orientation of the composite wing.